EP2703603B1 - Turbine blade of a gas turbine with swirl generating element and method for their production - Google Patents

Turbine blade of a gas turbine with swirl generating element and method for their production Download PDF

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Publication number
EP2703603B1
EP2703603B1 EP13182339.5A EP13182339A EP2703603B1 EP 2703603 B1 EP2703603 B1 EP 2703603B1 EP 13182339 A EP13182339 A EP 13182339A EP 2703603 B1 EP2703603 B1 EP 2703603B1
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EP
European Patent Office
Prior art keywords
swirl
turbine blade
generating element
blade
accordance
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP13182339.5A
Other languages
German (de)
French (fr)
Other versions
EP2703603A2 (en
EP2703603A3 (en
Inventor
Knut Dr. Lehmann
Tijana Filipova
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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Publication date
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Publication of EP2703603A2 publication Critical patent/EP2703603A2/en
Publication of EP2703603A3 publication Critical patent/EP2703603A3/en
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Publication of EP2703603B1 publication Critical patent/EP2703603B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade

Definitions

  • the invention relates to a turbine blade of a gas turbine and a method for their production.
  • the invention relates to a turbine blade of a gas turbine having a blade end arranged on a blade, which has at least one extending in the longitudinal direction of the turbine blade, arranged in the turbine blade cooling air passage which extends through the blade root.
  • One from the DE 100 53 356 A1 known turbine blade has for efficient internal cooling an inner leading edge cooling channel with a circular channel cross-section and over the length of the cooling channel stacked cooling air supply holes, which open from a formed in the blade coolant passage substantially tangentially in the leading edge cooling channel and generate in this cooling air vortex to achieve a high cooling effect.
  • the swirl flow thus formed does not develop optimally over the entire length of the cooling air duct.
  • the flow phenomena effective for cooling such as the return core and the boundary layer instabilities, are not optimally designed.
  • Another disadvantage is that the overall structure has a lower strength due to the many recesses.
  • An air-cooled gas turbine blade is known in which a swirl body is inserted in a cavity of the finished blade, wherein the swirl body is mounted after the completion of the blade, before the blade is connected to a disc or a wheel rim.
  • the swirler extends over a substantial length of the interior of the blade.
  • the invention has for its object to provide a turbine blade of the type mentioned above and a method for their preparation, which ensures a simple design and simple, cost-effective manufacturability and high mechanical strength optimizing the heat transfer of the air flowing through the cooling air duct.
  • At least one swirl-generating element which is preferably formed as a separate element, is arranged in the transitional area between the blade root and the airfoil in the cooling air duct.
  • the invention thus describes a turbine blade with a blade end arranged on a blade root, which has at least one cooling air channel extending in the longitudinal direction of the turbine blade and thus extending radially with respect to the machine axis and arranged in the turbine blade, which extends through the blade root Transition region between the blade root and the blade in the cooling air passage at least one swirl generating element is arranged.
  • the invention thus relates to the generation of a swirl flow in a radially (with respect to the engine axis) extending cooling air passage in the turbine blade.
  • the swirl generation takes place in the bladed swirl-generating element, which is designed as a stator.
  • the swirl-generating element is arranged in the transition region between the blade root and the blade or at a suitable location in the blade root and causes a flow-optimized swirl generation or cyclone production. Since the swirl-generating element according to the invention is manufactured as a separate component and subsequently inserted into the turbine blade and fixed there, the production of the swirl-generating element can take place in a precise and fluid-optimized manner.
  • the swirl-generating element according to the invention is designed as a casting, it can be made in an advantageous manner from the same material as the turbine blade.
  • the swirl-generating element on an outer ring and a plurality of arranged on this swirl-producing vanes may preferably be connected to a central region.
  • the swirl-generating element which has the shape of a flat cylinder with its outer ring, along its vertical axis, or transversely to the cylinder axis, into the turbine blade and then rotate it at the desired position in the cooling air duct.
  • the swirl generating element may then be suitably fixed in the final position by means of a snap ring, clips, molded noses or the like. In this case, both the radial fixation in the blade is guaranteed, as well as a safeguard against rotation, so that the desired swirl flow is formed in an optimal manner.
  • the solution according to the invention is characterized by a number of significant advantages.
  • the reduced pressure loss results in a higher reserve pressure for the film cooling supply.
  • Another advantage is that, compared to the prior art, a simplified arrangement and design of the cooling air supply channels in the blade root and thus simplified casting geometries can be realized.
  • the solution according to the invention does not lead to a weakening of the mechanical properties of the turbine blade.
  • a cyclone cooling concept for the turbine blade can thus be realized, which is advantageous with regard to the flow conditions and the heat transfer and leads, for example, to a cooling-air saving, to a reduction in the surface temperature of the turbine blade and to an improved durability of the blading.
  • the swirl-generating element is produced as a separate component. This may, as mentioned, consist of the same or a different material than the turbine blade.
  • the swirl-generating element is inserted and positioned by the blade root in the interior of the turbine blade. The positioning can be done for example by latching by means of a latching nose or the like, wherein corresponding stops or projections are formed in the interior of the turbine blade.
  • the swirl-generating element when the swirl-generating element is inserted with its central axis in a direction transverse to a blade longitudinal axis position through the blade root is particularly advantageous. Since the recess in the blade root is usually not arbitrarily large and since the blade root has no round, but a rectangular cross-section, it is thus possible to dimension the recess of the blade root accordingly and insert the swirl-generating element.
  • the cross section of the interior of the turbine blade (cooling air channel or leading edge cooling air channel) expands.
  • the swirl-generating element is rotated and subsequently positioned so that its center axis is arranged substantially parallel to the blade longitudinal axis.
  • the swirl-generating element is already produced integrally therewith during the casting process of the turbine blade. It is particularly advantageous if the swirl-generating element in a core, which for the production of the cooling air duct or the leading edge cooling air duct the turbine blade is used, is formed. Such cores are usually made as ceramic cores. In the procedure according to the invention, therefore, after the chemical dissolution of the ceramic core, the swirl-generating element is formed at the correct position in the interior of the turbine blade.
  • the gas turbine engine 10 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and a Exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the turbine of a gas turbine engine includes a plurality of turbine blades 30 connected to a rotor disk 29 and upstream thereon, attached to the engine casing 31, which are cooled by external cooling (film cooling) and internal cooling with compressor-supplied cooling air indicated by arrows 33 ,
  • the turbine blade 30 has a blade root 34 held on the rotor disk 29, an inner platform 35, an airfoil 36 and an outer platform 37.
  • the airfoil 36 formed as a hollow body for internal cooling is formed with cooling channels and film cooling holes 38 and air outlet openings 39 on the blade tip.
  • Cooling air passes from the cavity 41, located below the platforms 37 between two adjacent turbine blades 30, from two opposite sides (suction side and pressure side) into the lower section of an inside through an air supply duct 40 extending from the opposite sides of the blade root 34 the turbine blade 30 from the blade root 34 to the blade tip along the blade leading edge extending leading edge cooling channel 42 (FIGS. Fig. 4 to 7 ).
  • the cooling air 33 supplied to the leading edge cooling duct 42 flows outward over the film cooling bores 38 provided for the external cooling of the airfoil 36 and the air outlet openings 39 to the outside and / or into further cooling ducts (not shown) located in the airfoil 36.
  • the Fig. 3 shows in perspective an inventive swirl-generating element 43, which has an outer ring 44 which is formed in the form of a flat cylinder. Integrally with the ring 44, swirl-producing vanes 45 are connected, which are designed to be aerodynamically favorable. A central region 46 connects the radially inner end portions of the swirl-producing vanes 45.
  • the Fig. 3 shows the inflow side in the left-hand illustration and the outflow side of the swirl-generating element according to the invention in the right-hand illustration.
  • the reference numeral 49 shows a locking recess, which serves to make the latching of the swirl-generating element by means of a latching nose 50, which is formed in the cooling air passage 42.
  • the Fig. 4 to 7 each show in the side view and in the front view, the individual assembly steps for introducing the swirl-generating element 43 according to the invention in the cooling air passage 42.
  • the swirl-generating element 43 is pushed edgewise through the blade root in the cooling air passage 42.
  • the Fig. 5a and 5b show an assembly step in which the swirl-generating element 43 is located in the blade root.
  • the Fig. 6a and 6b show a subsequent mounting state in which the swirl-generating element 43 is tilted to this in the in the Fig. 7a and 7b shown final position at the transition region of the cooling air channel 42 from the blade root 34 to fix in the airfoil 36.
  • the fixation is done for example by means of abutment rings, noses, snap elements or the like.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung bezieht sich auf eine Turbinenschaufel einer Gasturbine sowie ein Verfahren zu deren Herstellung.The invention relates to a turbine blade of a gas turbine and a method for their production.

Im Einzelnen bezieht sich die Erfindung auf eine Turbinenschaufel einer Gasturbine mit einem an einem Schaufelfuß angeordneten Schaufelblatt, welches zumindest einen in Längsrichtung der Turbinenschaufel verlaufenden, in der Turbinenschaufel angeordneten Kühlluftkanal aufweist, welcher sich durch den Schaufelfuß erstreckt.In detail, the invention relates to a turbine blade of a gas turbine having a blade end arranged on a blade, which has at least one extending in the longitudinal direction of the turbine blade, arranged in the turbine blade cooling air passage which extends through the blade root.

Aus dem Stand der Technik ist es bekannt, die in den Kühlluftkanal eintretende Luftströmung mit einem Drall zu versehen, um den Wärmeübergang und damit die Kühlung zu verbessern.From the prior art, it is known to provide the air flow entering the cooling air duct with a swirl in order to improve the heat transfer and thus the cooling.

Eine aus der DE 100 53 356 A1 bekannte Turbinenschaufel weist zur effizienten Innenkühlung einen innen liegenden Vorderkantenkühlkanal mit rundem Kanalquerschnitt und über die Länge des Kühlkanals übereinander angeordnete Kühlluftzuführungsbohrungen auf, die von einem in der Schaufel ausgebildeten Kühlmittelkanal im Wesentlichen tangential in den Vorderkantenkühlkanal münden und in diesem Kühlluftwirbel zur Erzielung einer hohen Kühlwirkung erzeugen. Bei dieser Konstruktion ergibt sich der Nachteil, dass sich die so gebildete Drallströmung nicht optimal über die gesamte Länge des Kühlluftkanals entwickelt. Somit sind die zur Kühlung effektiven Strömungsphänomene, wie etwa der Rückstromkern und die Grenzschichtinstabilitäten nicht optimal ausgebildet. Ein weiterer Nachteil besteht darin, dass die Gesamtstruktur durch die vielen Ausnehmungen eine geringere Festigkeit aufweist.One from the DE 100 53 356 A1 known turbine blade has for efficient internal cooling an inner leading edge cooling channel with a circular channel cross-section and over the length of the cooling channel stacked cooling air supply holes, which open from a formed in the blade coolant passage substantially tangentially in the leading edge cooling channel and generate in this cooling air vortex to achieve a high cooling effect. In this construction, there is the disadvantage that the swirl flow thus formed does not develop optimally over the entire length of the cooling air duct. Thus, the flow phenomena effective for cooling, such as the return core and the boundary layer instabilities, are not optimally designed. Another disadvantage is that the overall structure has a lower strength due to the many recesses.

In der EP 1 621 730 A1 wird eine Lösung beschrieben, bei welcher in dem Kühlluftkanal schraubenförmig angeordnete Rippen ausgebildet sind, welche die Strömung in einen Drall versetzen sollen. Diese Konstruktion weist jedoch den Nachteil auf, dass es nur zu einer unzureichenden Drallströmung kommt, da nur kleine Drallzahlen erreicht werden können. Durch den hohen Anstellwinkel der Rippen weicht die Strömung zur Mitte aus, so dass die Rippen hauptsächlich als Turbulatoren wirken. Im Übrigen ist eine derartige Konstruktion sehr aufwendig in der Herstellung.In the EP 1 621 730 A1 describes a solution in which in the cooling air duct helically arranged ribs are formed, which are to put the flow in a twist. However, this design has the disadvantage that it comes only to an insufficient swirl flow, since only small swirl numbers can be achieved. Due to the high angle of attack of the ribs, the flow deviates from the center, so that the ribs act mainly as turbulators. Incidentally, such a construction is very expensive to manufacture.

Weiterhin wurde vorgeschlagen, durch eine tangentiale Einströmung in einem Kanal im Schaufelfuß eine Drallströmung oder Zyklonströmung zu erzeugen. Hierbei ergeben sich jedoch relativ hohe aerodynamische Verluste.It has also been proposed to generate a swirling flow or cyclone flow by means of a tangential inflow in a channel in the blade root. However, this results in relatively high aerodynamic losses.

Aus der DE 853 534 B ist eine luftgekühlte Gasturbinenschaufel bekannt, bei welcher in einem Hohlraum der fertiggestellten Schaufel ein Drallkörper eingesetzt ist, wobei der Drallkörper nach der Fertigstellung der Schaufel montiert wird, bevor die Schaufel mit einer Scheibe oder einem Radkranz verbunden wird. Der Drallkörper erstreckt sich über eine wesentliche Länge des Innenraums der Schaufel.From the DE 853 534 B An air-cooled gas turbine blade is known in which a swirl body is inserted in a cavity of the finished blade, wherein the swirl body is mounted after the completion of the blade, before the blade is connected to a disc or a wheel rim. The swirler extends over a substantial length of the interior of the blade.

Ferner ist aus der DE 698 17 094 T2 eine Turbinenschaufel gemäß dem Oberbegriff des Anspruchs 1 bekannt.Furthermore, from the DE 698 17 094 T2 a turbine blade according to the preamble of claim 1 known.

Der Erfindung liegt die Aufgabe zugrunde, eine Turbinenschaufel der eingangs genannten Art sowie ein Verfahren zu deren Herstellung zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit sowie hoher mechanischer Festigkeit eine Optimierung des Wärmeübergangs der durch den Kühlluftkanal strömenden Luft gewährleistet.The invention has for its object to provide a turbine blade of the type mentioned above and a method for their preparation, which ensures a simple design and simple, cost-effective manufacturability and high mechanical strength optimizing the heat transfer of the air flowing through the cooling air duct.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombinationen der unabhängigen Ansprüche gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the combination of features of the independent claims, the subclaims show further advantageous embodiments of the invention.

Erfindungsgemäß ist somit vorgesehen, dass im Übergangsbereich zwischen Schaufelfuß und Schaufelblatt in dem Kühlluftkanal zumindest ein Drallerzeugungselement angeordnet ist, welches bevorzugt als separates Element ausgebildet ist. Die Erfindung beschreibt somit eine Turbinenschaufel mit einem an einem Schaufelfuß angeordneten Schaufelblatt, welches zumindest einen in Längsrichtung der Turbinenschaufel verlaufenden, und somit sich radial, bezogen auf die Maschinenachse erstreckenden, in der Turbinenschaufel angeordneten Kühlluftkanal aufweist, welcher sich durch den Schaufelfuß erstreckt, wobei im Übergangsbereich zwischen Schaufelfuß und Schaufelblatt in dem Kühlluftkanal zumindest ein Drallerzeugungselement angeordnet ist.According to the invention, it is thus provided that at least one swirl-generating element, which is preferably formed as a separate element, is arranged in the transitional area between the blade root and the airfoil in the cooling air duct. The invention thus describes a turbine blade with a blade end arranged on a blade root, which has at least one cooling air channel extending in the longitudinal direction of the turbine blade and thus extending radially with respect to the machine axis and arranged in the turbine blade, which extends through the blade root Transition region between the blade root and the blade in the cooling air passage at least one swirl generating element is arranged.

Die Erfindung bezieht sich somit auf die Erzeugung einer Drallströmung in einem radial (bezogen auf die Triebwerksachse) verlaufenden Kühlluftkanal in der Turbinenschaufel. Damit findet erfindungsgemäß die Drallerzeugung in dem beschaufelten Drallerzeugungselement statt, welches als Leitrad ausgebildet ist. Das Drallerzeugungselement ist im Übergangsbereich zwischen dem Schaufelfuß und dem Schaufelblatt oder an geeigneter Stelle im Schaufelfuß angeordnet und bewirkt eine strömungsoptimierte Drallerzeugung oder Zyklonerzeugung. Da das erfindungsgemäße Drallerzeugungselement als separates Bauteil gefertigt und nachfolgend in die Turbinenschaufel eingesetzt und dort fixiert wird, kann die Herstellung des Drallerzeugungselements in präziser und strömungstechnisch optimierter Weise erfolgen. Bevorzugt ist das Drallerzeugungselement erfindungsgemäß als Gussteil ausgebildet, es kann in vorteilhafter Weise aus demselben Material wie die Turbinenschaufel gefertigt werden.The invention thus relates to the generation of a swirl flow in a radially (with respect to the engine axis) extending cooling air passage in the turbine blade. Thus, according to the invention, the swirl generation takes place in the bladed swirl-generating element, which is designed as a stator. The swirl-generating element is arranged in the transition region between the blade root and the blade or at a suitable location in the blade root and causes a flow-optimized swirl generation or cyclone production. Since the swirl-generating element according to the invention is manufactured as a separate component and subsequently inserted into the turbine blade and fixed there, the production of the swirl-generating element can take place in a precise and fluid-optimized manner. Preferably, the swirl-generating element according to the invention is designed as a casting, it can be made in an advantageous manner from the same material as the turbine blade.

In bevorzugter Ausgestaltung der Erfindung weist das Drallerzeugungselement einen äußeren Ring sowie mehrere an diesem angeordnete drallerzeugende Leitschaufeln auf. Diese können in bevorzugter Weise mit einem zentrischen Bereich verbunden sein.In a preferred embodiment of the invention, the swirl-generating element on an outer ring and a plurality of arranged on this swirl-producing vanes. These may preferably be connected to a central region.

In einer alternativen Ausgestaltung der Erfindung ist es jedoch auch möglich, anstelle eines separaten Drallerzeugungselements dieses einstückig mit der Schaufel auszubilden und somit bevorzugterweise beim Guß der Schaufel mitzuerzeugen.In an alternative embodiment of the invention, however, it is also possible, instead of a separate swirl-generating element, to form it integrally with the blade and thus to co-generate it during the casting of the blade.

Bei der Verwendung eines separaten Drallerzeugungselements ist es besonders vorteilhaft, dass dieses nachträglich in die Turbinenschaufel eingebracht und dort fixiert werden kann. Dadurch ist es möglich, das Drallerzeugungselement, welches mit seinem äußeren Ring die Form eines flachen Zylinders aufweist, entlang seiner Hochachse, beziehungsweise quer zur Zylinderachse, in die Turbinenschaufel einzuführen und dann an einer bestimmten Position im Kühlluftkanal in die gewünschte Lage zu drehen. Das Drallerzeugungselement kann dann in geeigneter Weise mittels eines Sprengrings, mittels Clips, mittels angegossener Nasen oder in ähnlicher Weise, in der endgültigen Position fixiert werden. Dabei ist sowohl die radiale Fixierung in der Schaufel gewährleistet, als auch eine Sicherung gegen Verdrehen, so dass sich die gewünschte Drallströmung in optimaler Weise ausbildet.When using a separate swirl-generating element, it is particularly advantageous that this can be subsequently introduced into the turbine blade and fixed there. This makes it possible to introduce the swirl-generating element, which has the shape of a flat cylinder with its outer ring, along its vertical axis, or transversely to the cylinder axis, into the turbine blade and then rotate it at the desired position in the cooling air duct. The swirl generating element may then be suitably fixed in the final position by means of a snap ring, clips, molded noses or the like. In this case, both the radial fixation in the blade is guaranteed, as well as a safeguard against rotation, so that the desired swirl flow is formed in an optimal manner.

Die erfindungsgemäße Lösung zeichnet sich durch eine Reihe erheblicher Vorteile aus. Zunächst ergibt sich ein verringerter Druckverlust bei der Erzeugung einer Zyklonströmung, verglichen mit den aus dem Stand der Technik bekannten Lösungen. Durch den verringerten Druckverlust ergibt sich ein höherer Reservedruck für die Filmkühlungsversorgung. Ein weiterer Vorteil besteht darin, dass, im Vergleich zum Stand der Technik, eine vereinfachte Anordnung und Ausgestaltung der Kühlluftversorgungskanäle im Schaufelfuß und damit vereinfachte Gussgeometrien realisiert werden können. Weiterhin führt die erfindungsgemäße Lösung nicht zu einer Schwächung der mechanischen Eigenschaften der Turbinenschaufel. Erfindungsgemäß kann somit ein Zyklonkühlungskonzept für die Turbinenschaufel realisiert werden, welches hinsichtlich der Strömungsverhältnisse und des Wärmeüberganges vorteilhaft ist und beispielsweise zu einer Kühllufteinsparung, zu einer Senkung der Oberflächentemperatur der Turbinenschaufel sowie zu einer verbesserten Haltbarkeit der Beschaufelung führt.The solution according to the invention is characterized by a number of significant advantages. First, there is a reduced pressure loss in the generation of a cyclone flow as compared to the solutions known from the prior art. The reduced pressure loss results in a higher reserve pressure for the film cooling supply. Another advantage is that, compared to the prior art, a simplified arrangement and design of the cooling air supply channels in the blade root and thus simplified casting geometries can be realized. Furthermore, the solution according to the invention does not lead to a weakening of the mechanical properties of the turbine blade. According to the invention, a cyclone cooling concept for the turbine blade can thus be realized, which is advantageous with regard to the flow conditions and the heat transfer and leads, for example, to a cooling-air saving, to a reduction in the surface temperature of the turbine blade and to an improved durability of the blading.

Hinsichtlich des erfindungsgemäßen Herstellungsverfahrens zur Herstellung der Turbinenschaufel ist in einer ersten Variante der Erfindung vorgesehen, dass das Drallerzeugungselement als separates Bauteil gefertigt wird. Dieses kann, wie erwähnt, aus dem selben oder einem anderen Werkstoff als die Turbinenschaufel bestehen. Nach der Fertigung der Turbinenschaufel wird erfindungsgemäß das Drallerzeugungselement durch den Schaufelfuß in den Innenraum der Turbinenschaufel eingeführt und positioniert. Die Positionierung kann beispielsweise durch Verrastung mittels einer Rastnase oder ähnlichem erfolgen, wobei entsprechende Anschläge oder Vorsprünge in dem Innenraum der Turbinenschaufel ausgebildet sind.With regard to the manufacturing method according to the invention for producing the turbine blade, in a first variant of the invention it is provided that the swirl-generating element is produced as a separate component. This may, as mentioned, consist of the same or a different material than the turbine blade. After the manufacture of the turbine blade according to the invention, the swirl-generating element is inserted and positioned by the blade root in the interior of the turbine blade. The positioning can be done for example by latching by means of a latching nose or the like, wherein corresponding stops or projections are formed in the interior of the turbine blade.

Besonders vorteilhaft ist es, wenn das Drallerzeugungselement mit seiner Mittelachse in einer zu einer Schaufellängsachse querliegenden Position durch den Schaufelfuß eingeschoben wird. Da die Ausnehmung im Schaufelfuß üblicherweise nicht beliebig groß ist und da der Schaufelfuß keinen runden, sondern einen rechteckigen Querschnitt aufweist, ist es somit möglich, die Ausnehmung des Schaufelfußes entsprechend zu dimensionieren und das Drallerzeugungselement einzuschieben. Im Übergangsbereich vom Schaufelfuß zum Schaufelblatt erweitert sich erfindungsgemäß der Querschnitt des Innenraums der Turbinenschaufel (Kühlluftkanal bzw. Vorderkanten-Kühlluftkanal). In diesem Bereich wird erfindungsgemäß das Drallerzeugungselement gedreht und nachfolgend so positioniert, dass seine Mittelachse im Wesentlichen parallel zur Schaufellängsachse angeordnet ist.It when the swirl-generating element is inserted with its central axis in a direction transverse to a blade longitudinal axis position through the blade root is particularly advantageous. Since the recess in the blade root is usually not arbitrarily large and since the blade root has no round, but a rectangular cross-section, it is thus possible to dimension the recess of the blade root accordingly and insert the swirl-generating element. In the transition region from the blade root to the blade, according to the invention, the cross section of the interior of the turbine blade (cooling air channel or leading edge cooling air channel) expands. In this area, according to the invention, the swirl-generating element is rotated and subsequently positioned so that its center axis is arranged substantially parallel to the blade longitudinal axis.

In einer weiteren Variante der Erfindung ist vorgesehen, dass das Drallerzeugungselement bereits während des Gussvorgangs der Turbinenschaufel einstückig mit dieser erzeugt wird. Hierbei ist es besonders vorteilhaft, wenn das Drallerzeugungselement in einem Kern, welcher zur Herstellung des Kühlluftkanals bzw. des Vorderkanten-Kühlluftkanals der Turbinenschaufel verwendet wird, ausgebildet ist. Derartige Kerne sind üblicherweise als Keramikkerne gefertigt. Bei der erfindungsgemäßen Vorgehensweise ist somit nach der chemischen Auflösung des Keramikkerns das Drallerzeugungselement an der richtigen Position im Inneren der Turbinenschaufel ausgebildet.In a further variant of the invention, it is provided that the swirl-generating element is already produced integrally therewith during the casting process of the turbine blade. It is particularly advantageous if the swirl-generating element in a core, which for the production of the cooling air duct or the leading edge cooling air duct the turbine blade is used, is formed. Such cores are usually made as ceramic cores. In the procedure according to the invention, therefore, after the chemical dissolution of the ceramic core, the swirl-generating element is formed at the correct position in the interior of the turbine blade.

Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:

Fig. 1
eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung;
Fig. 2
eine Leitschaufel- und Turbinenschaufelanordnung eines Flugtriebwerks;
Fig. 3
perspektivische Ansichten eines erfindungsgemäßen Drallerzeugungselements; und
Fig. 4 bis 7
einzelne Montageschritte des Drallerzeugungselements in einer Turbinenschaufel.
In the following the invention will be described by means of an embodiment in conjunction with the drawing. Showing:
Fig. 1
a schematic representation of a gas turbine engine according to the present invention;
Fig. 2
a vane and turbine blade assembly of an aircraft engine;
Fig. 3
perspective views of a swirl-generating element according to the invention; and
Fig. 4 to 7
individual assembly steps of the swirl-generating element in a turbine blade.

Das Gasturbinentriebwerk 10 gemäß Fig. 1 ist ein allgemein dargestelltes Beispiel einer Turbomaschine, bei der die Erfindung Anwendung finden kann. Das Triebwerk 10 ist in herkömmlicher Weise ausgebildet und umfasst in Strömungsrichtung hintereinander einen Lufteinlass 11, einen in einem Gehäuse umlaufenden Fan 12, einen Mitteldruckkompressor 13, einen Hochdruckkompressor 14, eine Brennkammer 15, eine Hochdruckturbine 16, eine Mitteldruckturbine 17 und eine Niederdruckturbine 18 sowie eine Abgasdüse 19, die sämtlich um eine zentrale Triebwerksachse 1 angeordnet sind.The gas turbine engine 10 according to Fig. 1 is a generalized example of a turbomachine, in which the invention can be applied. The engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and a Exhaust nozzle 19, which are all arranged around a central engine axis 1.

Der Zwischendruckkompressor 13 und der Hochdruckkompressor 14 umfassen jeweils mehrere Stufen, von denen jede eine in Umfangsrichtung verlaufende Anordnung fester stationärer Leitschaufeln 20 aufweist, die allgemein als Statorschaufeln bezeichnet werden und die radial nach innen vom Triebwerksgehäuse 21 in einem ringförmigen Strömungskanal durch die Kompressoren 13, 14 vorstehen. Die Kompressoren weisen weiter eine Anordnung von Kompressorlaufschaufeln 22 auf, die radial nach außen von einer drehbaren Trommel oder Scheibe 26 vorstehen, die mit Naben 27 der Hochdruckturbine 16 bzw. der Mitteldruckturbine 17 gekoppelt sind.The intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude. The compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.

Die Turbinenabschnitte 16, 17, 18 weisen ähnliche Stufen auf, umfassend eine Anordnung von festen Leitschaufeln 23, die radial nach innen vom Gehäuse 21 in den ringförmigen Strömungskanal durch die Turbinen 16, 17, 18 vorstehen, und eine nachfolgende Anordnung von Turbinenschaufeln 24, die nach außen von einer drehbaren Nabe 27 vorstehen. Die Kompressortrommel oder Kompressorscheibe 26 und die darauf angeordneten Schaufeln 22 sowie die Turbinenrotornabe 27 und die darauf angeordneten Turbinenlaufschaufeln 24 drehen sich im Betrieb um die Triebwerksachse 1.The turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27. The compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.

Wie Fig. 2 zeigt, umfasst die Turbine eines Gasturbinentriebwerks eine Mehrzahl von mit einer Rotorscheibe 29 verbundenen Turbinenschaufeln 30 und diesen stromauf zugeordneten, am Triebwerksgehäuse 31 angebrachten Leitschaufeln 32, die durch Außenkühlung (Filmkühlung) und Innenkühlung mit von einem Kompressor zugeführter, durch Pfeile 33 gekennzeichneter Kühlluft gekühlt werden. Die Turbinenschaufel 30 weist einen an der Rotorscheibe 29 gehaltenen Schaufelfuß 34, eine innere Plattform 35, ein Schaufelblatt 36 und eine äußere Plattform 37 auf. Das zur Innenkühlung als Hohlkörper ausgebildete Schaufelblatt 36 ist mit Kühlkanälen und Filmkühlbohrungen 38 sowie Luftaustrittsöffnungen 39 an der Schaufelspitze ausgebildet. Durch jeweils einen von den gegenüberliegenden Seiten des Schaufelfußes 34 ausgehenden Luftzuführungskanal 40 gelangt Kühlluft (Pfeil 33) aus dem unterhalb der Plattformen 37 zwischen zwei benachbarten Turbinenschaufeln 30 vorhandenen Hohlraum 41 von zwei gegenüberliegenden Seiten (saugseitig und druckseitig) in den unteren Abschnitt eines sich im Inneren der Turbinenschaufel 30 vom Schaufelfuß 34 bis zur Schaufelspitze entlang der Schaufelvorderkante erstreckenden Vorderkantenkühlkanals 42 (Fig. 4 bis 7). Die dem Vorderkantenkühlkanal 42 zugeführte Kühlluft 33 strömt über zur die Außenkühlung des Schaufelblattes 36 vorgesehenen Filmkühlbohrungen 38 und die Luftaustrittsöffnungen 39 nach außen und/oder in weitere im Schaufelblatt 36 befindliche Kühlkanäle (nicht dargestellt).As Fig. 2 1, the turbine of a gas turbine engine includes a plurality of turbine blades 30 connected to a rotor disk 29 and upstream thereon, attached to the engine casing 31, which are cooled by external cooling (film cooling) and internal cooling with compressor-supplied cooling air indicated by arrows 33 , The turbine blade 30 has a blade root 34 held on the rotor disk 29, an inner platform 35, an airfoil 36 and an outer platform 37. The airfoil 36 formed as a hollow body for internal cooling is formed with cooling channels and film cooling holes 38 and air outlet openings 39 on the blade tip. Cooling air (arrow 33) passes from the cavity 41, located below the platforms 37 between two adjacent turbine blades 30, from two opposite sides (suction side and pressure side) into the lower section of an inside through an air supply duct 40 extending from the opposite sides of the blade root 34 the turbine blade 30 from the blade root 34 to the blade tip along the blade leading edge extending leading edge cooling channel 42 (FIGS. Fig. 4 to 7 ). The cooling air 33 supplied to the leading edge cooling duct 42 flows outward over the film cooling bores 38 provided for the external cooling of the airfoil 36 and the air outlet openings 39 to the outside and / or into further cooling ducts (not shown) located in the airfoil 36.

Die Fig. 3 zeigt in perspektivischer Darstellung ein erfindungsgemäßes Drallerzeugungselement 43, welches einen äußeren Ring 44 aufweist, der in Form eines flachen Zylinders ausgebildet ist. Einstückig mit dem Ring 44 sind drallerzeugende Leitschaufeln 45 verbunden, welche strömungsgünstig ausgebildet sind. Ein zentrischer Bereich 46 verbindet die radial inneren Endbereiche der drallerzeugenden Leitschaufeln 45. Die Fig. 3 zeigt in der linken Darstellung die Anströmseite und in der rechten Darstellung die Abströmseite des erfindungsgemäßen Drallerzeugungselements.The Fig. 3 shows in perspective an inventive swirl-generating element 43, which has an outer ring 44 which is formed in the form of a flat cylinder. Integrally with the ring 44, swirl-producing vanes 45 are connected, which are designed to be aerodynamically favorable. A central region 46 connects the radially inner end portions of the swirl-producing vanes 45. The Fig. 3 shows the inflow side in the left-hand illustration and the outflow side of the swirl-generating element according to the invention in the right-hand illustration.

Das Bezugszeichen 49 zeigt eine Verriegelungsaussparung, welche dazu dient, die Verrastung des Drallerzeugungselements mittels einer Rastnase 50, welche in dem Kühlluftkanal 42 ausgebildet ist, vorzunehmen.The reference numeral 49 shows a locking recess, which serves to make the latching of the swirl-generating element by means of a latching nose 50, which is formed in the cooling air passage 42.

Die Fig. 4 bis 7 zeigen jeweils in der Seitenansicht und in der stirnseitigen Ansicht die einzelnen Montageschritte zur Einbringung des erfindungsgemäßen Drallerzeugungselements 43 in den Kühlluftkanal 42. Wie in den Fig. 4a und 4b dargestellt, wird das Drallerzeugungselement 43 hochkant durch den Schaufelfuß in den Kühlluftkanal 42 eingeschoben. Die Fig. 5a und 5b zeigen einen Montageschritt, bei welchem sich das Drallerzeugungselement 43 im Schaufelfuß befindet. Die Fig. 6a und 6b zeigen einen nachfolgenden Montagezustand, bei welchem das Drallerzeugungselement 43 gekippt wird, um dieses nachfolgend in die in den Fig. 7a und 7b gezeigte endgültige Lage am Übergangsbereich des Kühlluftkanals 42 vom Schaufelfuß 34 in das Schaufelblatt 36 zu fixieren. Die Fixierung erfolgt beispielsweise mittels Anlageringen, Nasen, Schnappelementen oder ähnlichem.The Fig. 4 to 7 each show in the side view and in the front view, the individual assembly steps for introducing the swirl-generating element 43 according to the invention in the cooling air passage 42. As in the Fig. 4a and 4b shown, the swirl-generating element 43 is pushed edgewise through the blade root in the cooling air passage 42. The Fig. 5a and 5b show an assembly step in which the swirl-generating element 43 is located in the blade root. The Fig. 6a and 6b show a subsequent mounting state in which the swirl-generating element 43 is tilted to this in the in the Fig. 7a and 7b shown final position at the transition region of the cooling air channel 42 from the blade root 34 to fix in the airfoil 36. The fixation is done for example by means of abutment rings, noses, snap elements or the like.

Bezugszeichenliste:LIST OF REFERENCE NUMBERS

11
TriebwerksachseEngine axis
1010
Gasturbinentriebwerk / KerntriebwerkGas turbine engine / core engine
1111
Lufteinlassair intake
1212
Fanfan
1313
Mitteldruckkompressor (Verdichter)Medium pressure compressor (compressor)
1414
HochdruckkompressorHigh pressure compressor
1515
Brennkammerncombustors
1616
HochdruckturbineHigh-pressure turbine
1717
MitteldruckturbineIntermediate pressure turbine
1818
NiederdruckturbineLow-pressure turbine
1919
Abgasdüseexhaust nozzle
2020
Leitschaufelnvanes
2121
TriebwerksgehäuseEngine casing
2222
KompressorlaufschaufelnCompressor blades
2323
Leitschaufelnvanes
2424
Turbinenschaufelnturbine blades
2626
Kompressortrommel oder -scheibeCompressor drum or disc
2727
TurbinenrotornabeTurbinenrotornabe
2828
Auslasskonusoutlet cone
2929
Rotorscheiberotor disc
3030
Turbinenschaufel / SchaufelblattTurbine blade / blade
3131
TriebwerksgehäuseEngine casing
3232
Leitschaufelnvanes
3333
Kühlluft, rotierende Kühlluftschicht (Pfeil)Cooling air, rotating cooling air layer (arrow)
3434
Schaufelfußblade
3535
innere Plattforminner platform
3636
Schaufelblattairfoil
3737
äußere Plattformouter platform
3838
FilmkühlbohrungFilm cooling hole
3939
LuftaustrittsöffnungAir outlet opening
4040
düsenförmiger Luftzuführungskanalnozzle-shaped air supply duct
4141
Hohlraumcavity
4242
Kühlluftkanal, VorderkantenkühlkanalCooling air duct, leading edge cooling duct
4343
DrallerzeugungselementSwirl-producing element
4444
Ringring
4545
drallerzeugende Leitschaufelspin-generating vane
4646
zentrischer Kanalcentric channel
4747
Mittelachse des DrallerzeugungselementsCentral axis of the swirl-generating element
4848
Schaufellängsachse der Turbinenschaufel 30Blade longitudinal axis of the turbine blade 30
4949
Verriegelungsaussparunglocking recess
5050
Rastnaselocking lug

Claims (13)

  1. Turbine blade (30) of a gas turbine with an airfoil (36) arranged on a blade root (34) and having at least one cooling air duct (42) running in the longitudinal direction of the turbine blade (30), arranged inside the turbine blade (30) and extending through the blade root (34), characterized in that at least one swirl-generating element (43) is arranged in the transitional area between blade root (34) and airfoil (36) in the cooling air duct (42), with the swirl-generating element (43) including an outer ring (44) and several swirl-generating stator vanes (45) arranged therein, which are connected to a centric area (46).
  2. Turbine blade in accordance with Claim 1, characterized in that inside the cooling air duct (42) at least one fixing element is provided that can be positively engaged with the swirl-generating element (43).
  3. Turbine blade in accordance with one of the Claims 1 or 2, characterized in that the outer ring (44) is dimensioned such that it can be inserted into the cooling air duct (42) from the blade root (34).
  4. Turbine blade in accordance with one of the Claims 1 or 2, characterized in that the swirl-generating element (43) is connected to the turbine blade (30) in one piece.
  5. Turbine blade in accordance with one of the Claims 1 to 4, characterized in that the swirl-generating element (43) is designed in the form of a guide vane arrangement imparting a swirl motion to the cooling airflow.
  6. Turbine blade in accordance with one of the Claims 1 to 5, characterized in that the swirl-generating element (43) is made from the same material as the turbine blade (30).
  7. Turbine blade in accordance with one of the Claims 1 to 6, characterized in that the swirl-generating element (43) is designed as a casting.
  8. Turbine blade in accordance with one of the Claims 1 to 7, characterized in that the swirl-generating element (43) is designed as part of a casting core.
  9. Method for manufacturing a turbine blade in accordance with one of the Claims 1 to 8, characterized in that the swirl-generating element (43) is manufactured as a separate component and is introduced through the blade root (34) and positioned after the manufacture of the turbine blade (30).
  10. Method in accordance with Claim 9, characterized in that the swirl-generating element (43) is inserted with its center axis (47) in a position transverse to a blade longitudinal axis (48), is rotated in the transitional area between blade root (34) and airfoil (36) and is positioned with its center axis (47) substantially parallel to the blade longitudinal axis (48).
  11. Method in accordance with Claim 9 or 10, characterized in that the swirl-generating element (43) is locked upon positioning.
  12. Method for manufacturing a turbine blade in accordance with one of the Claims 1 to 8, characterized in that the swirl-generating element (43) is produced in one piece with the turbine blade (30) during the casting process of the latter.
  13. Method in accordance with Claim 12, characterized in that the swirl-generating element (43) is provided in a core for the manufacture of the turbine blade (30) and remains after removal of the core as one-piece constituent of the turbine blade (30).
EP13182339.5A 2012-09-04 2013-08-30 Turbine blade of a gas turbine with swirl generating element and method for their production Not-in-force EP2703603B1 (en)

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US9618002B1 (en) * 2013-09-27 2017-04-11 University Of South Florida Mini notched turbine generator
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US9995151B2 (en) * 2015-08-17 2018-06-12 General Electric Company Article and manifold for thermal adjustment of a turbine component
EP3199759A1 (en) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Turbine blade for a thermal turbo engine
US10583489B2 (en) * 2017-04-26 2020-03-10 General Electric Company Method of providing cooling structure for a component
CN115234306A (en) * 2022-09-21 2022-10-25 中国航发燃气轮机有限公司 Gas turbine air-cooled blade

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JPS6099933A (en) * 1983-11-04 1985-06-03 Mitsubishi Heavy Ind Ltd Manufacture of swirler
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US20140079539A1 (en) 2014-03-20
US9506352B2 (en) 2016-11-29
EP2703603A3 (en) 2017-08-16
DE102012017491A1 (en) 2014-03-06

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